19982 Federal Register / Vol. 78, No. 64 / Wednesday, April 3, 2013 / Rules and Regulations 

FOR FURTHER INFORMATION CONTACT: Joe 

Jacobsen, FAA, Airplane and Flight 

Crew Interface Branch, ANM–111, 

Transport Airplane Directorate, Aircraft 

Certification Service, 1601 Lind Avenue 

SW., Renton, Washington 98057–3356; 

telephone 425–227–2011; facsimile 

425–227–1149. 

SUPPLEMENTARY INFORMATION: The 

document designated as ‘‘Docket No. 

FAA–2012–1215, Special Conditions 

No. 25–12–482–SC’’ was published in 

the Federal Register on February 19, 

2013 (78 FR 11562). The document 

issued special conditions pertaining 

flight envelope protection: high speed 

limiting. 

As published, the document 

contained an error in that the Special 

Conditions number. To avoid confusion, 

in the heading of this correction to the 

special conditions has been changed to 

the correct Special Conditions number, 

No. 25–482–SC. 

Since no other part of the regulatory 

information has been changed, the 

special conditions are not being 

republished. 

Correction 

In Final special conditions document 

[FR Doc. 2013–03676 Filed 2–15–13; 

8:45 am] published on February 19, 

2013 (78 FR 11562), make the following 

correction: 

■ On page 11562, in the third column, 

in the Headings section, correct 

‘‘Special Conditions No. 25–12–482– 

SC’’ to read ‘‘Special Conditions No. 25– 

482–SC.’’ 

Issued in Renton, Washington, on March 

28, 2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–07651 Filed 4–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 33 

[EDocket No. FAA–2012–1085; Special 

Conditions No. 33–013–SC] 

Special Conditions: Turbomeca 

Ardiden 3K Turboshaft Engine 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final special condition. 

SUMMARY: We are issuing these special 

conditions for the Turbomeca Ardiden 

3K model engines. This engine model 

will have a novel or unusual design 

feature that is a 30-minute all engines 

operating (AEO) power rating for 

hovering at increased power (HIP). This 

rating is primarily intended for highpower hovering operations that are 

normal mission functions. The 

applicable airworthiness regulations do 

not contain adequate or appropriate 

safety standards for this design feature. 

These special conditions contain the 

additional safety standards that the FAA 

considers necessary to establish a level 

of safety equivalent to that established 

by the existing airworthiness standards. 

DATES: The effective date of these 

special conditions is May 3, 2013. 

FOR FURTHER INFORMATION CONTACT: For 

technical questions concerning these 

special conditions, contact Tara 

Fitzgerald, ANE–111, Engine and 

Propeller Directorate, Aircraft 

Certification Service, 12 New England 

Executive Park, Burlington, 

Massachusetts 01803–5299; telephone: 

(781) 238–7130; facsimile: (781) 238– 

7199; email: tara.fitzgerald@faa.gov. For 

legal questions concerning these special 

conditions, contact Vincent Bennett, 

ANE–7 Engine and Propeller 

Directorate, Aircraft Certification 

Service, 12 New England Executive 

Park, Burlington, Massachusetts 01803– 

5299; telephone: (781) 238–7044; 

facsimile: (781) 238–7055; email: 

vincent.bennett@faa.gov. 

SUPPLEMENTARY INFORMATION:

Background 

On September 15, 2010, Turbomeca 

S.A. (Turbomeca) applied for a type 

certificate for their new Ardiden 3K 

turboshaft engine. The Ardiden 3K 

engine is the first variant in the new 

Ardiden 3 series. This engine 

incorporates a two-stage centrifugal 

compressor that is driven by a singlestage high-pressure turbine. A two-stage 

power turbine drives the engine output 

shaft. The control system includes a 

dual-channel full-authority digitalelectronic control. 

The engine will incorporate a novel or 

unusual design feature, which is a 30- 

minute hovering at increased power 

(HIP) rating. The applicant requested 

this rating to support extended hover 

operations at high power. 

Special conditions are necessary to 

apply additional requirements for rating 

definition, instructions for continued 

airworthiness (ICA), instrumentation, 

and endurance testing because the 

applicable airworthiness standards do 

not contain adequate or appropriate 

airworthiness standards to address this 

design feature. The ICA requirement 

addresses the unknown nature of actual 

rating usage and associated engine 

deterioration. The applicant is expected 

to assess the expected usage, and 

publish ICA and Airworthiness 

Limitations Section limits in accordance 

with those assumptions, such that 

engine deterioration is not excessive. 

The instrumentation requirement is to 

ensure that operators use this highpower rating within its limits, and that 

engine integrity is maintained. The 

endurance test requirement of 25 hours 

operation at 30-minutes HIP is similar to 

other special conditions recently issued. 

Because the Ardiden 3K model has a 

continuous one engine inoperative (OEI) 

rating with limits equal to or higher 

than the proposed 30-minute HIP rating, 

the applicant may credit the test time 

performed at the continuous OEI rating 

toward the 25-hour requirement. 

However, test time spent at other rating 

elements of the test, such as takeoff or 

other OEI ratings (that are equal to or 

higher than HIP rating values), cannot 

be counted toward the 25 hours of 

required running. 

These special conditions contain the 

additional airworthiness standards 

necessary to establish a level of safety 

equivalent to the level intended by the 

applicable standards of airworthiness in 

effect on the date of application. 

Type Certification Basis 

Under the provisions of 14 CFR 21.17 

and 21.101(a), Turbomeca must show 

that the model Ardiden 3K turboshaft 

engine meets the provisions of the 

applicable regulations in effect on the 

date of application, or later amendment 

if so elected. Accordingly, the 

certification basis for the Ardiden model 

turboshaft engine is determined to be 

part 33, effective February 1, 1965, as 

amended by Amendments 33–1 through 

33–31. 

If because of a novel or unusual 

design feature, we find that the 

applicable airworthiness regulations in 

part 33, as amended, do not contain 

adequate or appropriate safety standards 

for the Turbomeca model Ardiden 3K 

turboshaft engine, special conditions are 

prescribed under the provisions of 

§ 21.16. 

We issue special conditions, as 

defined by 14 CFR 11.19, under 14 CFR 

11.38, which become part of the type 

certification basis as specified in 

§ 21.17(a)(2). 

Special conditions are initially 

applicable to the model for which they 

are issued. If the type certificate for that 

model is amended later to include 

another related model that incorporates 

the same or similar novel or unusual 

design feature, or if any other model 

already included on the same type 

certificate is modified to incorporate the 


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Federal Register / Vol. 78, No. 64 / Wednesday, April 3, 2013 / Rules and Regulations 19983 

same or similar novel or unusual design 

feature, the special conditions would 

also apply to the other model. 

Novel or Unusual Design Features 

The Turbomeca model Ardiden 3K 

turboshaft engine will incorporate a 30- 

minute HIP rating, for use up to 30 

minutes at any time between take-off 

and landing. The 30-minute time limit 

applies to each instance the rating is 

used. However, there is no limit to the 

number of times the rating can be used 

during any one flight and there is no 

cumulative time limitation. These 

special conditions for a 30-minute HIP 

rating apply to address this novel and 

unusual design feature. 

Discussion of Comments 

A notice of proposed special 

conditions, Notice 33–12–02–SC for the 

Turbomeca model Ardiden 3K 

turboshaft engine was published on 

November 8, 2012 (77 FR 66936). We 

received no comments. 

Applicability 

These special conditions are 

applicable to Turbomeca model Ardiden 

3K turboshaft engines. If Turbomeca 

applies later for a change to the type 

certificate to include another closely 

related model incorporating the same 

novel or unusual design feature, these 

special conditions would apply to that 

model as well. This is true, if the 

certification basis is the same or 

contains later amendments that satisfy 

the certification basis discussed in the 

section titled ‘‘Type Certification Basis.’’ 

Conclusion 

We reviewed the available data and 

have determined that air safety and the 

public interest require adopting these 

special conditions as proposed. This 

action affects certain novel or unusual 

design features on the Turbomeca 

Model Ardiden 3K turboshaft engine. It 

is not a rule of general applicability, and 

applies only to Turbomeca, that 

requested FAA approval for these 

engine features. 

List of Subjects in 14 CFR part 33 

Air transportation, Aircraft, Aviation 

safety, Safety. 

■ The authority citation for these 

special conditions continues to read as 

follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701– 

44702, 44704. 

The Special Conditions 

■ Accordingly, the FAA issues the 

following special conditions as part of 

the type certification basis for the 

Turbomeca model Ardiden 3K 

turboshaft engine. 

1. Part 1 Definitions 

Unless otherwise approved by the 

Administrator and documented in the 

appropriate manuals and certification 

documents, the following definition 

applies to these special conditions: 

‘‘Rated 30-Minute Hover at Increased 

Power (HIP),’’ means the approved shaft 

horsepower developed under static 

conditions at the specified altitude and 

temperature, and within the operating 

limitations established under part 33, 

and limited in use to periods not 

exceeding 30 minutes. 

2. Part 33 Requirements 

(a) Sections 33.1 Applicability and 

33.3 General. As applicable, all 

documentation, testing and analysis 

required to comply with the part 33 

certification basis must account for the 

30-minute HIP rating, limits, and usage. 

(b) Section 33.4, Instructions for 

Continued Airworthiness (ICA). In 

addition to the requirements of § 33.4, 

the ICA must: 

(1) Include instructions to ensure that 

in-service engine deterioration due to 

rated 30-minute HIP usage will not be 

excessive, meaning that all approved 

ratings, including One Engine 

Inoperative (OEI), are available (within 

associated limits and assumed usage) for 

each flight; and that deterioration will 

not exceed that assumed for declaring a 

Time Between Overhaul period. 

(2) Validate the adequacy of the 

maintenance actions required under 

paragraph (b)(1) above. 

(3) Include in the Airworthiness 

Limitations section, any mandatory 

inspections and serviceability limits 

related to the use of the 30-minute HIP 

rating. 

(c) Section 33.29, Instrument 

Connection. The engine must have a 

means or a provision for a means, which 

alerts the pilot when the 30-minute HIP 

rating time limit has expired. 

(d) Section 33.87, Endurance Test. In 

addition to the applicable requirements 

of §§ 33.87(a), 33.87(d) and 33.87(e) (for 

engines that combine 2.5 minute and 

continuous OEI ratings): 

(1) The overall test run must include 

a minimum of 25 hours of operation at 

30-minute HIP rating and limits, 

divided into periods of not less than 30 

minutes but not more than 60 minutes, 

with alternate periods at maximum 

continuous power or less. 

(2) Each § 33.87(d)(3) continuous OEI 

rating test period of 60 minutes duration 

run at power and limits equal to or 

higher than the 30-minute HIP rating, 

may be credited toward this 

requirement. Note that you may not 

count the test time required for the 

takeoff or other OEI ratings toward the 

25 hours of testing required at the 30- 

minute HIP rating. 

Issued in Burlington, Massachusetts, on 

March 5, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–07662 Filed 4–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1288; Directorate 

Identifier 2012–NE–37–AD; Amendment 39– 

17403; AD 2013–06–06] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for General 

Electric Company (GE) CF34–8C and 

CF34–8E turbofan engines with certain 

part numbers (P/N) of operability bleed 

valves (OBV) installed. This AD was 

prompted by three failure events of ring 

lock fuel fittings on the OBV. Two of 

those events led to an engine fire. This 

AD requires the affected OBVs be 

removed from service and replaced with 

OBVs eligible for installation. We are 

issuing this AD to prevent failure of 

OBV ring lock fuel fittings, engine fuel 

leakage, uncontrolled fire, and damage 

to the airplane. 

DATES: This AD is effective May 8, 2013. 

ADDRESSES: For service information 

identified in this AD, contact General 

Electric Company, One Neumann Way, 

MD Y–75, Cincinnati, OH; phone: 513– 

552–2913; email: geae.aoc@ge.com; and 

Web site: www.GE.com. You may view 

the referenced service information at the 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA. For information on the 

availability of this material at the FAA, 

call 781–238–7125. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 


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